US8221060B2 - Sealing means - Google Patents
Sealing means Download PDFInfo
- Publication number
- US8221060B2 US8221060B2 US12/457,743 US45774309A US8221060B2 US 8221060 B2 US8221060 B2 US 8221060B2 US 45774309 A US45774309 A US 45774309A US 8221060 B2 US8221060 B2 US 8221060B2
- Authority
- US
- United States
- Prior art keywords
- location
- sealing
- segment
- sealing member
- compressor vane
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active, expires
Links
- 238000007789 sealing Methods 0.000 title claims abstract description 129
- 230000013011 mating Effects 0.000 claims abstract description 30
- 230000007704 transition Effects 0.000 claims abstract description 17
- 239000007767 bonding agent Substances 0.000 claims description 11
- 238000000034 method Methods 0.000 claims description 9
- 239000002131 composite material Substances 0.000 claims description 7
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 5
- 239000000853 adhesive Substances 0.000 claims description 5
- 230000001070 adhesive effect Effects 0.000 claims description 5
- 229910052799 carbon Inorganic materials 0.000 claims description 5
- 229920001971 elastomer Polymers 0.000 claims description 5
- 239000000806 elastomer Substances 0.000 claims description 5
- 238000011144 upstream manufacturing Methods 0.000 claims description 4
- 239000000428 dust Substances 0.000 claims description 3
- 239000000835 fiber Substances 0.000 claims description 3
- 229920001973 fluoroelastomer Polymers 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 2
- 229920001296 polysiloxane Polymers 0.000 claims description 2
- 230000003068 static effect Effects 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/55—Seals
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/55—Seals
- F05D2240/57—Leaf seals
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
- Y10T156/10—Methods of surface bonding and/or assembly therefor
Definitions
- the present invention relates to a sealing means for sealing between components of a component assembly.
- the invention is concerned with a sealing means comprising a sealing member with a detachable location member for sealing between components of a component assembly.
- a conventional fan and/or compressor assembly includes rotor blades interspaced with static vane stages which occupy a duct which defines a path down which fluid being pressurised will pass.
- a gap is provided between the rotatable and static components to permit relative rotation.
- it is important to minimise this gap in order to limit leakage of the air being pressurised.
- this is achieved by either designing the gap to be as small as possible and/or by the provision of a sealing member which extends across at least part of the width of the gap.
- a thin metal sealing member is located in a groove in the stator vane platform. The sealing member obstructs the gas flow through the gap and is thin enough that, in the event of excessive relative axial movement of the stator vane and rotor blade, it is easily deformed without causing damage to the vane or blade.
- the edge of the groove in the platform in which the sealing member steps down to the sealing member since the edge of the groove in the platform in which the sealing member steps down to the sealing member, it will inherently introduce a discontinuity into the gas washed surface of the platform, thus introducing a disturbance to the flow. Also, in builds where a composite vane is used to reduce weight of the system, a groove in the platform will significantly reduce the strength of the vane and may result in composite structure coming apart.
- the location of the sealing member is critical, since it must provide a seal without interfering with the gas flow over the platform. That is to say, it must occupy a location predefined in the design of the compressor and be neither too far inset or too proud of the gas washed surfaces of adjacent platforms. In the absence of a location groove, this is achieved using dedicated jigs, fixtures and tooling to which are expensive to produce and time consuming to use.
- a sealing means for sealing between segments of a component assembly comprising
- the advantage of this arrangement is that the sealing member can be easily and accurately located on a component without the need for a dedicated location feature.
- the location feature may be any feature on the segment of the component. Any existing feature can be used, including features provided for functions which are entirely unconnected to the present invention. That is to say, any feature on the surface of the segment can be employed as a location feature provided it has a fixed location relative to the position on the segment where the sealing member is to be mated to the segment. Thus no dedicated location feature on the segment is required to locate the sealing member. This is particularly advantageous for segments made from composite materials as having a continuous surface without location features, such as holes or groove, will maintain the integrity of the vane.
- a compressor vane segment for a compressor vane array comprising a sealing member provided on at least one of the upstream or downstream edges of the vane segments.
- This product and method provide the advantage that the sealing means can be located accurately and precisely on rotor blade and stator vane platform segments without the need for providing dedicated location features.
- FIG. 1 shows a section of a fan and compressor according to the present invention
- FIG. 2 is an enlarged perspective view of a stator vane platform of the compressor shown in FIG. 1 showing a sealing member;
- FIG. 3 is a section through the platform shown in FIG. 2 ;
- FIG. 4 is a perspective view of the platform of FIGS. 2 and 3 partway through its manufacturing process with the sealing member and its respective location member;
- FIG. 5 is a section through the platform shown in FIG. 4 ;
- FIG. 6 is a perspective “front” view of the platform with an alternative embodiment of a sealing member and location member according to the present invention.
- FIG. 7 is perspective “rear” view of the platform, sealing member and location member of FIG. 6 .
- FIG. 1 shows a section of a fan 10 and compressor section 12 of a gas turbine engine according to the present invention.
- the compressor 12 comprises rows of rotor blade segments 14 interspaced with static vane stage segments 16 .
- a casing 18 defines a bypass duct 20 and an intake 22 in which the blades 14 and vanes 16 are located.
- the blade segments 14 and vane segments 16 each comprise a platform 24 , 26 respectively, and a gap 28 is provided between the platforms 24 , 26 to permit relative rotation.
- the vane platforms 24 each terminate in a leg 30 to which is attached a sealing land 32 for sealing against a labyrinth seal 34 provided on a shaft 36 to which the rotor blades 14 are mounted.
- a sealing member 40 according to the present invention is provided on at least one of the upstream or downstream edges of the platforms 24 the vane segments 16 .
- the sealing member 40 has a mating surface 42 which is bonded to a mating surface 44 of the platform 24 .
- the sealing member has a “T” cross section, with an outer flat portion 46 of the “T” providing the mating surface 42 and a leg portion 48 extending substantially at right angles away from the mating surface 42 .
- the leg portion 48 tapers to a point at an end distal to the mating surface 42 and flat portion 46 .
- the sealing member 40 is sized to extend across the gap 28 between the blade 14 and vane 16 platforms 24 , 26 . In use, the sealing member 40 dissuades air passing from the intake 22 between the blade 14 and vane 15 platforms 24 , 26 .
- the vane 16 and platform 24 is made from a composite material, for example an organic matrix carbon composite. With such a structure it is beneficial to avoid stress raising features like grooves and holes to locate and fix the sealing member 40 in a desired location on the platform 24 .
- a sealing means 50 according to the present invention comprising the sealing member 40 and a location member 52 allows for the sealing member 40 to be accurately located on the platform 24 .
- the sealing means 50 comprises the location member 52 removably attached to the sealing member 40 along at a transition region 54 therebetween.
- the location member 52 has a free end 56 distal to the sealing member 40 and is configured to engage a location feature 58 of the vane segment 16 , which in this embodiment is the free end of leg 30 .
- the location member 52 conforms to the shape of the surface of the segment 16 in the region where it engages with the segment 16 , and is hook shaped to fit around the leg portion 30 and thus locate the mating surface 42 of the sealing member 40 in a fixed position on the mating 44 surface of the segment platform 24 relative to the free end of the leg portion 30 .
- the location member 52 is configured to be detached from the sealing member 40 along the transition region 54 and removed from the vane segment 16 after the sealing member 40 has been bonded to the vane segment 16 .
- the transition region 54 is provided with a weakened region 60 which divides the sealing member 40 and location member 52 .
- the sealing means 50 that is to say, the sealing member 40 and location member 52 , are formed integrally from the same material.
- the sealing member 40 and location member 52 are made from an elastomer.
- the elastomer comprises silicone reinforced with carbon fibre dust, where the carbon fibre dust increases the wear resistance of the sealing member 40 .
- the mating surface 42 of the sealing member 40 is bonded to the mating surface 44 of the vane segment 16 by a bonding agent.
- the bonding agent is preferably a fluoro elastomer adhesive.
- the sealing member 40 is attached to the platform 24 by a process including the steps of applying a bonding agent to the mating surface 42 of the sealing member 40 and engaging the location member 52 with the location feature 30 on the segment 16 to thereby locate the sealing member 40 in a fixed position on the surface 44 of the segment 16 relative to the location feature 30 .
- Heat and/or pressure is then applied to the mating surfaces 42 , 44 so as to achieve bonding between the sealing member 40 and segment 16 .
- the location member 52 is then disengaged from the location feature 30 and detached from the sealing member 40 along the transition region 54 .
- the weakened region 60 provides a discrete line along which the sealing means 50 can be cut and/or torn to detach the location member 52 from the sealing member 40 .
- FIGS. 6 and 7 A further embodiment of the present invention is shown in FIGS. 6 and 7 .
- the sealing means 50 is identical to the sealing means of FIGS. 4 and 5 , other than at least one weakened region 62 extends at an angle from the transition region 54 towards free end 56 of the location member 52 .
- This provides a number of sectors 64 which can be removed from the leg 30 , thus making the overall operation of removing location member 52 easier. Also sectors 64 of the location member 52 can be removed prior to engagement with the location member 30 to avoid distortion of the sealing means 50 should the radius of the arc of the platform 24 be small.
- the sealing means 50 can be provided as a continuous strip or in segmented in pieces sized to fit each vane segment 16 .
- the present invention ensures the sealing member 40 can be located quickly and easily during manufacture of the vane segment 16 , and thus eliminates the need for location features such as grooves or holes in the surface of the platform 24 , as well as obviating the need for expensive and complex jigs, fixtures or tooling to position the sealing member 40 in the correct location.
- the location member 52 guarantees correct axial and radial location of the sealing member 40 . Since the location member 52 is removed after the sealing member 40 has been bonded in place, the feature used as a location feature, in this case the free end 58 of the leg portion 30 , can subsequently be used as intended without modification to other components. In this example, this means the sealing land 32 can be mounted on the leg portions 30 without modification.
- sealing means 50 and method of assembly according to the present invention ensure the sealing member 40 cannot be fitted incorrectly as the location feature 52 will only permit assembly in one orientation.
Abstract
Description
- a sealing member having a mating surface for mating with the surface of the segment;
- a location member removably attached to the sealing member along a transition region therebetween and having a free end distal to the sealing member,
- the location member being configured to engage a location feature of the segment so as to locate the mating surface of the sealing member in a fixed position on the surface of the segment relative to the location feature,
- the location member being configured to be detached from the sealing member along the transition region and removed from the segment after the sealing member has been bonded to the segment.
- a) applying a bonding agent to the mating surface of the sealing member;
- b) engaging the location member with the location feature on the segment, thereby locating the sealing member in a fixed position on the surface of the segment relative to the location feature;
- c) applying heat and/or pressure to the mating surface so as to achieve a bond between the sealing member and segment; and
- d) disengaging the location member from the location feature and detach the location member from the sealing member along the transition region.
Claims (22)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB0814981.7 | 2008-08-18 | ||
GB0814981A GB2462810B (en) | 2008-08-18 | 2008-08-18 | Sealing means |
Publications (2)
Publication Number | Publication Date |
---|---|
US20100040463A1 US20100040463A1 (en) | 2010-02-18 |
US8221060B2 true US8221060B2 (en) | 2012-07-17 |
Family
ID=39812129
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/457,743 Active 2030-10-21 US8221060B2 (en) | 2008-08-18 | 2009-06-19 | Sealing means |
Country Status (3)
Country | Link |
---|---|
US (1) | US8221060B2 (en) |
EP (1) | EP2157288B1 (en) |
GB (1) | GB2462810B (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20140227088A1 (en) * | 2011-09-07 | 2014-08-14 | Herakles | Assembly formed by a turbine nozzle or a compressor diffuser made of cmc for a turbine engine and by an abradable material support ring, and a turbine or a compressor incorporating such an assembly |
US20170328203A1 (en) * | 2016-05-10 | 2017-11-16 | General Electric Company | Turbine assembly, turbine inner wall assembly, and turbine assembly method |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8225614B2 (en) * | 2010-10-07 | 2012-07-24 | General Electric Company | Shim for sealing transition pieces |
WO2015088593A1 (en) * | 2013-12-13 | 2015-06-18 | United Technologies Corporation | Fan platform edge seal |
Citations (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3248081A (en) | 1964-12-29 | 1966-04-26 | Gen Electric | Axial locating means for airfoils |
US5480162A (en) * | 1993-09-08 | 1996-01-02 | United Technologies Corporation | Axial load carrying brush seal |
US5667224A (en) * | 1996-05-14 | 1997-09-16 | General Atomics | Adjustable seal assembly |
US5693288A (en) * | 1994-06-24 | 1997-12-02 | Nisshin Steel Co., Ltd. | Seal assembly for thermal treatment furnaces using an atmospheric gas containing hydrogen gas |
US5957658A (en) * | 1997-04-24 | 1999-09-28 | United Technologies Corporation | Fan blade interplatform seal |
US6260854B1 (en) | 1998-10-09 | 2001-07-17 | Georg Fischer Rohleitungssysteme Ag | Flat gasket ring |
US6312218B1 (en) * | 1998-10-19 | 2001-11-06 | Asea Brown Boveri Ag | Sealing arrangement |
US6398499B1 (en) * | 2000-10-17 | 2002-06-04 | Honeywell International, Inc. | Fan blade compliant layer and seal |
US20040145124A1 (en) | 2003-01-24 | 2004-07-29 | Yoakam John Arthur | Seal and retainer for a fluid connection |
EP1914389A1 (en) * | 2006-10-20 | 2008-04-23 | Siemens Aktiengesellschaft | Turbine blade with separated seal element |
US20100152700A1 (en) * | 2006-11-17 | 2010-06-17 | Novartis Ag | Integrated storage and delivery systems for nutritional compositions |
US7918643B2 (en) * | 2006-06-07 | 2011-04-05 | Rolls-Royce Plc | Sealing arrangement in a gas turbine engine |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4002344A (en) * | 1975-11-12 | 1977-01-11 | Smith Franklyn D | Snap-in flange seal and locator |
FR2775328B1 (en) * | 1998-02-26 | 2000-04-28 | Christian Loth | SEAL FOR PIPE FLANGE |
US20080044284A1 (en) * | 2006-08-16 | 2008-02-21 | United Technologies Corporation | Segmented fluid seal assembly |
-
2008
- 2008-08-18 GB GB0814981A patent/GB2462810B/en not_active Expired - Fee Related
-
2009
- 2009-06-15 EP EP09251561.8A patent/EP2157288B1/en not_active Not-in-force
- 2009-06-19 US US12/457,743 patent/US8221060B2/en active Active
Patent Citations (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3248081A (en) | 1964-12-29 | 1966-04-26 | Gen Electric | Axial locating means for airfoils |
US5480162A (en) * | 1993-09-08 | 1996-01-02 | United Technologies Corporation | Axial load carrying brush seal |
US5693288A (en) * | 1994-06-24 | 1997-12-02 | Nisshin Steel Co., Ltd. | Seal assembly for thermal treatment furnaces using an atmospheric gas containing hydrogen gas |
US5667224A (en) * | 1996-05-14 | 1997-09-16 | General Atomics | Adjustable seal assembly |
US5957658A (en) * | 1997-04-24 | 1999-09-28 | United Technologies Corporation | Fan blade interplatform seal |
US6260854B1 (en) | 1998-10-09 | 2001-07-17 | Georg Fischer Rohleitungssysteme Ag | Flat gasket ring |
US6312218B1 (en) * | 1998-10-19 | 2001-11-06 | Asea Brown Boveri Ag | Sealing arrangement |
US6398499B1 (en) * | 2000-10-17 | 2002-06-04 | Honeywell International, Inc. | Fan blade compliant layer and seal |
US20040145124A1 (en) | 2003-01-24 | 2004-07-29 | Yoakam John Arthur | Seal and retainer for a fluid connection |
US7364166B2 (en) * | 2003-01-24 | 2008-04-29 | Applied Engineered Surfaces, Inc. | Seal and retainer for a fluid connection |
US7918643B2 (en) * | 2006-06-07 | 2011-04-05 | Rolls-Royce Plc | Sealing arrangement in a gas turbine engine |
EP1914389A1 (en) * | 2006-10-20 | 2008-04-23 | Siemens Aktiengesellschaft | Turbine blade with separated seal element |
US20100152700A1 (en) * | 2006-11-17 | 2010-06-17 | Novartis Ag | Integrated storage and delivery systems for nutritional compositions |
Non-Patent Citations (1)
Title |
---|
Bergander, Turbine Blade With Separated Seal Element, Apr. 23, 2008, EP1914389 abstract. * |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20140227088A1 (en) * | 2011-09-07 | 2014-08-14 | Herakles | Assembly formed by a turbine nozzle or a compressor diffuser made of cmc for a turbine engine and by an abradable material support ring, and a turbine or a compressor incorporating such an assembly |
US9822655B2 (en) * | 2011-09-07 | 2017-11-21 | Snecma | Assembly formed by a turbine nozzle or a compressor diffuser made of CMC for a turbine engine and by an abradable material support ring, and a turbine or a compressor incorporating such an assembly |
US20170328203A1 (en) * | 2016-05-10 | 2017-11-16 | General Electric Company | Turbine assembly, turbine inner wall assembly, and turbine assembly method |
Also Published As
Publication number | Publication date |
---|---|
US20100040463A1 (en) | 2010-02-18 |
GB2462810A (en) | 2010-02-24 |
GB2462810B (en) | 2010-07-21 |
GB0814981D0 (en) | 2008-09-24 |
EP2157288A2 (en) | 2010-02-24 |
EP2157288A3 (en) | 2013-04-17 |
EP2157288B1 (en) | 2016-06-15 |
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Owner name: ROLLS-ROYCE PLC,GREAT BRITAIN Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:SLATER, RICHARD MARTIN;WOODFIELD, ROBERT WILLIAM;REEL/FRAME:022887/0901 Effective date: 20090430 Owner name: ROLLS-ROYCE PLC, GREAT BRITAIN Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:SLATER, RICHARD MARTIN;WOODFIELD, ROBERT WILLIAM;REEL/FRAME:022887/0901 Effective date: 20090430 |
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